WO2016181051A1 - Device with radial shaft for controlling the orientation of the fan blades of an unducted fan turbomachine - Google Patents
Device with radial shaft for controlling the orientation of the fan blades of an unducted fan turbomachine Download PDFInfo
- Publication number
- WO2016181051A1 WO2016181051A1 PCT/FR2016/051016 FR2016051016W WO2016181051A1 WO 2016181051 A1 WO2016181051 A1 WO 2016181051A1 FR 2016051016 W FR2016051016 W FR 2016051016W WO 2016181051 A1 WO2016181051 A1 WO 2016181051A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blades
- orientation
- shaft
- control shaft
- eccentric
- Prior art date
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- 230000005540 biological transmission Effects 0.000 claims abstract description 19
- 230000033001 locomotion Effects 0.000 claims description 17
- 230000001131 transforming effect Effects 0.000 claims 1
- 238000011144 upstream manufacturing Methods 0.000 description 14
- 230000008859 change Effects 0.000 description 8
- 238000010586 diagram Methods 0.000 description 6
- 230000001141 propulsive effect Effects 0.000 description 5
- 230000007423 decrease Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/306—Blade pitch-changing mechanisms specially adapted for contrarotating propellers
- B64C11/308—Blade pitch-changing mechanisms specially adapted for contrarotating propellers automatic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- Radial shaft device for controlling the orientation of the fan blades of a non-ducted fan turbomachine
- the present invention relates to the general field of turbomachines equipped with one or two fan (s) not careened (s), and more particularly to the control of the orientation of the fan blades (s) of these turbomachines.
- a preferred field of application of the invention relates to turbojet engines with counter-rotating propellers, called “Open Rotors” in English, which comprise two counter-rotating propellers placed downstream (“pusher” version in English) or upstream (“puller” version). in English) of the gas generator.
- the invention also applies to turboprop engines with one or more propulsive propellers.
- the control mechanism of the orientation of the propeller blades of the turbojet engine is generally integrated inside the hub carrying the propellers. More specifically, the orientation of each blade constituting the propellers is typically controlled by a rotary radial shaft which is connected to a fixed jack centered on the longitudinal axis of the turbojet engine via a motion transfer bearing, the displacement of the cylinder rod causing a rotation of the radial shaft around its axis.
- a rotary radial shaft which is connected to a fixed jack centered on the longitudinal axis of the turbojet engine via a motion transfer bearing, the displacement of the cylinder rod causing a rotation of the radial shaft around its axis.
- WO 2013/050704 describes an example of implementation of such a command.
- one of the solutions envisaged for improving the propulsive efficiency of the propeller of a jet propeller with contra-rotating propellers is to reduce the propeller hub ratio, that is to say the ratio between the diameter taken at the bottom of the blades of the propeller and the diameter taken at their top.
- the propeller hub ratio is to say the ratio between the diameter taken at the bottom of the blades of the propeller and the diameter taken at their top.
- the present invention therefore has the main purpose of providing a device for controlling the orientation of the blades which does not have the aforementioned drawbacks.
- a device for controlling the orientation of the fan blades of a non-ducted fan turbomachine comprising at least one set of adjustable-orientation fan blades, said assembly being integral in rotation with a ring.
- rotary assembly centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade of the assembly being mounted on a blade root support pivotally mounted on the rotary ring, and which according to the invention further comprises at least one radial control shaft for adjusting the orientation of at least two adjacent blades of the assembly, said control shaft being integral in rotation with the rotary ring and able to pivot about an axis of the shaft being coupled to the blade foot supports of the at least two blades of the assembly to adjust their orientation via a transmission system comprising eccentric interconnected by at least one connecting rod.
- the control device according to the invention is remarkable in particular that it provides to use the same radial control shaft for adjusting the orientation of at least two adjacent fan blades.
- Such an arrangement makes it possible to introduce an offset (in the tangential direction) between the control shaft and the two adjacent fan blades whose orientation it controls.
- the control shaft can be mounted from outside the rotating ring, and not from the inside thereof.
- the total number of control shafts becomes much smaller than the total number of fan blades (reduction by at least 2), which reduces the congestion problems inside the rotary ring.
- it is possible to reduce the hub ratio of the fan of the turbomachine, and thus to increase the propulsive efficiency and reduce the associated fuel consumption.
- the reduction of the total number of control shafts by means of the device according to the invention makes it possible to reduce the number of rotating caster arms traversed by these control shafts.
- the gas flow that passes through the vein traversed by the rotating casing arms is increased.
- each transmission system is located in the vicinity of the foot of said blades.
- the device can thus comprise, for each drive shaft, a driving eccentric which is mounted at an outer end of the control shaft and a driven eccentric which is mounted on each of the two blade root supports and which is connected to the eccentric leading by at least one connecting rod.
- the driving eccentric and the two driven eccentrics have centers of rotation that form a triangle (that is, they are not aligned with each other).
- eccentric leading and the two driven eccentrics may have centers of rotation which are aligned in the same plane perpendicular to a motor axis.
- the connecting rods of the device are connected to eccentrics leading and preferably conducted by ball joints.
- each transmission system may include a driving eccentric which is mounted at an outer end of the drive shaft and a driven eccentric which is mounted on each of the two blade foot supports, the driven eccentrics being interconnected by a connecting rod and one of the driven eccentrics being connected to the eccentric leading by another connecting rod.
- each control shaft is coupled to the blade foot supports of at least three adjacent blades of the assembly to adjust their orientation, the foot support of one of the blades being coupled to the control shaft. by a system of splines in direct engagement with said control shaft and the foot support of the other two blades being coupled to the control shaft by the transmission system.
- the device may further comprise a cylinder centered on a longitudinal axis of the turbomachine and a system for converting the axial movement of the cylinder into a rotational movement of each control shaft about its axis.
- the invention also relates to a non-ducted fan turbomachine, comprising at least one set of adjustable-orientation fan blades and at least one device for controlling the orientation of the blades as defined above.
- FIG. 1 is a schematic longitudinal sectional view of a jet engine with contra-rotating propellers to which the invention applies;
- FIG. 2 is a block diagram of a control device according to one embodiment of the invention.
- FIGS. 3A and 3B are partial kinematic diagrams of the control device of FIG. 2 according to a first variant embodiment
- FIGS. 4A and 4B are partial kinematic diagrams of the control device of FIG. 2 according to a second variant embodiment
- FIG. 5 is a partial kinematic diagram of a control device according to a third embodiment more particularly applicable to the control of the orientation of the blades of a single propeller of a turboprop;
- FIG. 6 is a block diagram of a control device according to another embodiment of the invention. Detailed description of the invention
- the invention applies to any turbomachine equipped with at least one non-ducted fan, in particular turboprop engines with one or more propulsive propellers, as well as jet engines with counter-rotating propellers (called “Open Rotors” in English) which comprise two counter-rotating propellers placed upstream (in version "puller” in English) or downstream (in “pusher” version in English) of the gas generator, such as the turbojet 2 of the "pusher” type shown schematically in FIG.
- the turbojet engine 2 comprises, from upstream to downstream in the direction of flow of the gas flow inside a nacelle 4 of the turbojet, one or two compressors 6 (according to the architecture of the gas generator to single or double body), a combustion chamber 8, a high-pressure turbine 10 (or a high-pressure turbine and an intermediate pressure turbine according to said architecture), and a low-pressure turbine 12 which contra-rotatingly drives, by means of a gearbox or epicyclic gearbox 14, an upstream propeller 16 and a downstream propeller 18 which are aligned coaxially along the longitudinal axis XX of the turbojet and which are arranged downstream of the combustion chamber.
- the upstream propeller 16 is integral with a rotary ring 20 centered on the longitudinal axis XX of the turbojet and rotatably coupled to an output of the gearbox 14 to rotate in one direction, while the downstream propeller 18 is secured to another rotating ring 22 also centered on the axis XX and rotatably coupled to another output of the reducer 14 to rotate in an opposite direction.
- the coupling between the gearbox outputs and the rotary rings of the propellers is known and is therefore not detailed here.
- the blades 26 of the upstream propeller 16 and the blades 28 of the downstream propeller 18 each have a foot which is mounted on a blade foot support, respectively 30, 32, these blade foot supports being they are pivotally mounted on the corresponding rotary ring 20, 22.
- a rotation of the blade foot supports around the stacking axis of the blades they carry allows to adjust the orientation of the latter (we also speak of pitch change pitch blades).
- the turbojet engine 2 also comprises a device according to the invention for controlling the orientation of the blades of each propeller 16, 18.
- a device for controlling the orientation of the blades 26 of the upstream propeller 16 is represented in such a way schematic in Figure 2.
- this device is equally applicable to the orientation of the blades of the downstream propeller of the turbojet engine.
- the control device comprises in particular a plurality of radial control shafts 34 (that is to say which are arranged radially with respect to the longitudinal axis XX of the turbojet engine), each control shaft 34 being provided for the adjustment of the orientation of at least two adjacent blades 26 of the upstream propeller 16.
- FIG. 2 represents an upstream propeller comprising twelve blades 26 whose orientation is controlled by six radial control shafts 34.
- the control shafts 34 for the upstream propeller 16 are integral in rotation with the rotary ring 20 rotating said propeller and on which the blade foot supports 30 are mounted.
- the control device also comprises means for pivoting each control shaft 34 about its axis 34a and with respect to the rotary ring 20.
- axis 34a of the shaft is meant here the axis of revolution of the cylindrical portion of said control shaft.
- these means comprise in particular a fixed jack 36 centered on the longitudinal axis XX of the turbojet and a system for converting the axial movement of the jack in a rotational movement of each control shaft about its axis, by For example, a motion transfer bearing 38.
- a motion transfer bearing 38 for example, a motion transfer bearing 38.
- the control device further comprises transmission systems 100 of the pivoting movement of the control shafts 34 about their respective axis 34a in a pivoting of the blade foot supports of the two adjacent blades, each of which they control the orientation.
- FIGS. 3A-3B show a first embodiment of the kinematics of a transmission system 100 of the pivoting movement of a control shaft 34 in a pivoting of the blade foot supports 30 of two adjacent blades 26 which it controls orientation.
- control shaft 34 passes through the rotary ring at a pivot connection 102.
- a driving eccentric 104 (symbolized in the figures by a plate) is centered on a outer end of this control shaft and the blade foot support 30 of the two blades controlled by it are each mounted on a driven eccentric 106 (also symbolized in the figures by a plate).
- Each plate (or eccentric) led 106 is connected to the driving plate 104 by a connecting rod 108 by means of two ball joints 110, 112 (one at each end of the connecting rod 108).
- the arrangement of the rods 108 is configured such that a pivoting of the driving plate 104 about the axis 34a of the control shaft which carries it causes a corresponding pivoting in the same direction of the two trays (or eccentrics) conducted 106 around their axis of revolution, the latter being coincident with a wedge axis 26a of the corresponding blades.
- a pivoting of the control shaft 34 about its axis 34a causes a change in the orientation (i.e. a change of pitch) of the two adjacent blades 26 that it drives.
- the centers of rotation of the leading and driven plates, respectively 01 for the driving plate 104 and O2 for the driven plates 106, of this first variant are not aligned with each other (in a tangential direction YY relative to the longitudinal axis XX of the turbojet engine). On the contrary, these centers of rotation form a triangle whose vertices are the centers of gravity Ol, O2 of these plates 104, 106.
- the centers O2 led trays 106 and the center Ol of the driving plate 104 are respectively on the same first plane perpendicular to the motor axis and a second plane axially offset relative to the first plane.
- the three centers of the trays thus form an isosceles triangle and the lengths of connecting rods are substantially equal to the side of this triangle so that the system makes it possible to have a symmetrical (or quasi-symmetrical) rotational movement between two consecutive blades.
- the wheel carrying the control shafts 34 for the upstream propeller 16 of the turbojet can be axially offset (along the longitudinal axis XX) relative to the upstream propeller.
- an axial offset for the downstream propeller 18 of the turbojet it is thus possible to de-correlate the spacing between the two control shaft wheels and the distance between the two sets of fan blades.
- This latitude makes it possible to optimize the mechanical integration of the control device according to the invention inside the turbojet engine.
- FIGS. 4A-4B show a second embodiment of the kinematics of a transmission system 100 'of the pivoting movement of a control shaft 34 in a pivoting of the blade foot supports 30 of two adjacent blades 26 which it command the orientation.
- the second embodiment differs from the first described above in that the center of rotation 01 'of the plate (or eccentric) leading 104' and the centers of rotation O2 'of the two trays (or eccentric) led 106' are aligned according to one line (relative to the tangential direction YY - see Figure 4B). In other words, these centers of rotation belong to the same plane perpendicular to the motor axis.
- each driven plate 106 ' is connected to the driving plate 104' by a rod 108 'by means of two ball joints 110', 112 '(one at each end of the connecting rod 108').
- the arrangement of these rods 108 ' is also configured such that a pivoting of the driving plate 104' about the axis 34a of the control shaft 34 which carries it causes a corresponding pivoting in the same direction of the two plates conducted 106 'around the wedge axis 26a 26 corresponding blades.
- a pivoting of the control shaft 34 about its axis 34a causes a change in the orientation (i.e. a change of pitch) of the two adjacent blades 26 that it drives.
- FIG. 5 schematically illustrates a third embodiment of the kinematics of a transmission system 100 "of the pivoting movement of a control shaft in a pivoting of the blade foot supports of two adjacent blades 26 which it controls. orientation.
- the transmission system 100 "comprises, for each drive shaft, a driving plate (or eccentric) 104 which is mounted at an outer end of the control shaft and a driven plate (or eccentric) 106 which is mounted on each of the two foot supports of the two adjacent blades.
- the driven trays 106 are here interconnected by a first connecting rod 118 (via ball joints 120), and one of the driven trays is connected to the driving plate 104 by a second connecting rod 122 (also via ball joints 124).
- the arrangement of the connecting rods 118, 122 is configured such that a pivoting of the driving plate 104 about the axis of the control shaft which carries it causes a corresponding pivoting in the same direction of the driven plate 106 coupled directly to the plateau leading to the second connecting rod 122, this pivoting causing a corresponding pivoting in the same direction of the other driven plate 106 by the first connecting rod 118.
- FIG. 6 represents a block diagram of a control device according to another embodiment of the invention.
- control device also comprises a plurality of radial control shafts 34 ', with the difference that each control shaft 34 'is here coupled to the blade foot supports of three adjacent blades 26 of the propeller 16 to adjust their orientation (ie change their pitch).
- Figure 6 shows an upstream propeller 16 comprising nine blades 26 whose orientation is controlled by three radial control shafts 34 '. These control shafts 34 'are integral in rotation with the rotary ring 20 rotating the propeller 16 and on which are mounted the blade foot supports (not shown in Figure 6).
- each control shaft 34 'about its axis 34'a and with respect to the rotary ring 20 are identical to those described in connection with the previous embodiment, namely that they may comprise, for example a fixed jack 36 centered on the longitudinal axis XX of the turbojet engine and a motion transfer bearing 38 for converting the axial movement of the jack 36 into a rotational movement of each control shaft 34 'about its axis.
- the control device also comprises transmission systems 100 'of the pivoting movement of the control shafts 34' around their respective axes 34'a in a pivoting of the blade foot supports of the three blades, each of which they control the orientation.
- the foot support of the blade whose wedge axis 26a coincides with the axis 34'a of the control shaft is coupled to said shaft by a system 114 of grooves in direct engagement with the shaft, and the foot support of the other two blades directly adjacent to the previous one is coupled to the shaft control system by driving / driven eccentric systems 116 and connecting rods.
- the system 114 is a system known to man by which splines carried by the upper end of the control shaft 34 'mesh corresponding grooves carried by the foot support of the blade.
- the system 116 it is a mechanism substantially identical to that described in connection with FIGS. 4A-4B in which the upper end of the control shaft carries a plate (or eccentric) leading centered on the shaft 34'a of the shaft, this driving plate being coupled (by ball joints) to two trays (or eccentric) led each linked to one of the two adjacent blades of the triplet of blades.
- a pivoting of the control shaft 34 'about its axis 34'a causes a modification of the orientation (or a change of pitch) of the three adjacent blades which it controls, either by the system 114 to splines, either by the eccentric system 116 leading / driven and connecting rods.
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Abstract
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Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/573,163 US11225317B2 (en) | 2015-05-12 | 2016-04-29 | Radial shaft device for controlling the pitch of fan blades of a turbine engine having an un-ducted fan |
GB1718651.1A GB2554015B (en) | 2015-05-12 | 2016-04-29 | A radial shaft device for controlling the pitch of fan blades of a turbine engine having an un-ducted fan |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1554275 | 2015-05-12 | ||
FR1554275A FR3036092B1 (en) | 2015-05-12 | 2015-05-12 | RADIAL ARRAY DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A NON-CARBONATED BLOWER TURBOMACHINE |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016181051A1 true WO2016181051A1 (en) | 2016-11-17 |
Family
ID=53758403
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2016/051016 WO2016181051A1 (en) | 2015-05-12 | 2016-04-29 | Device with radial shaft for controlling the orientation of the fan blades of an unducted fan turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US11225317B2 (en) |
FR (1) | FR3036092B1 (en) |
GB (1) | GB2554015B (en) |
WO (1) | WO2016181051A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3112809B1 (en) * | 2020-07-23 | 2022-07-29 | Safran Aircraft Engines | TURBOMACHINE MODULE EQUIPPED WITH A PROPELLER AND STATOR VANE SUPPORTED BY HOLDING MEANS AND CORRESPONDING TURBOMACHINE |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1554279A (en) | 1968-02-09 | 1969-01-17 | ||
FR1554280A (en) | 1967-02-09 | 1969-01-17 | ||
WO2010136684A1 (en) * | 2009-05-29 | 2010-12-02 | Snecma | Stationary actuator device for controlling the orientation of the blades of a turboprop fan |
GB2492882A (en) * | 2011-07-13 | 2013-01-16 | Snecma | A device for controlling the pitch of turboprop fan blades |
WO2013050704A1 (en) | 2011-10-03 | 2013-04-11 | Snecma | Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1979616A (en) * | 1934-04-28 | 1934-11-06 | Haidle Fred | Propeller control |
US2029503A (en) * | 1935-06-29 | 1936-02-04 | Axel Nelson | Automatic change pitch propeller |
-
2015
- 2015-05-12 FR FR1554275A patent/FR3036092B1/en active Active
-
2016
- 2016-04-29 US US15/573,163 patent/US11225317B2/en active Active
- 2016-04-29 GB GB1718651.1A patent/GB2554015B/en active Active
- 2016-04-29 WO PCT/FR2016/051016 patent/WO2016181051A1/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1554280A (en) | 1967-02-09 | 1969-01-17 | ||
FR1554279A (en) | 1968-02-09 | 1969-01-17 | ||
WO2010136684A1 (en) * | 2009-05-29 | 2010-12-02 | Snecma | Stationary actuator device for controlling the orientation of the blades of a turboprop fan |
GB2492882A (en) * | 2011-07-13 | 2013-01-16 | Snecma | A device for controlling the pitch of turboprop fan blades |
WO2013050704A1 (en) | 2011-10-03 | 2013-04-11 | Snecma | Turbo engine with propeller(s) for an aircraft with a system for changing the pitch of the propeller |
Also Published As
Publication number | Publication date |
---|---|
GB2554015A (en) | 2018-03-21 |
US20180065730A1 (en) | 2018-03-08 |
GB2554015B (en) | 2021-03-10 |
FR3036092B1 (en) | 2017-06-02 |
US11225317B2 (en) | 2022-01-18 |
GB201718651D0 (en) | 2017-12-27 |
FR3036092A1 (en) | 2016-11-18 |
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